Control-surface-mounted landing and taxi lights
A lighting assembly for movable control surfaces of a vehicle. The light assembly includes a lens, a plurality of light-emitting diodes (LEDs) and a housing that receives the plurality of LEDs and the lens. The housing of the light assembly is received within the movable control surface, such that the lens is flush with a surface of the movable control surface. The light assembly includes a plurality of reflectors. The plurality of LEDs is rotatably mounted within the housing. The light assembly includes a controller that controls the position of the LEDs relative to the housing, based on a received control signal.
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Forward-facing aircraft floodlight placement is currently limited to small areas of fixed structure, landing gear, landing gear doors, or extendable lights—see
Recently, high-intensity discharge (HID) lamps have been substituted for traditional PAR-46- and PAR-64-sized lamps. While the HID lamps are somewhat smaller for a given output, than the older PAR lamps, the packaging requirements are similar and have required placement within the traditional aircraft locations.
Traditional aircraft locations for forward lighting represent several engineering challenges. Any equipment mounted on the landing gear is subject to damage and wear from airflow, driven water, fluid leakage, shock loads, vibration, and mechanical stress from failing components or ground equipment contact. Placing extendable or gear-mounted lighting in the airstream increases aerodynamic drag. During the landing phase of flight, aerodynamic drag within reason is not a significant problem. However, any extra drag after take-off, while climbing out, is harmful.
Landing lights are used for added conspicuity whenever the aircraft is below a defined altitude. This is true both out-bound and inbound, as well as in an orbiting pattern. This defined altitude ranges from 18,000 to 10,000, feet based on local requirements. In many cases an aircraft is operating below the altitude that requires switching on a landing light yet prior to lowering the landing gear. Lights mounted in the wing root/strakelet area or retractable lights are normally used before the landing gear is lowered.
SUMMARY OF THE INVENTIONThe present invention provides an array of solid-state light-emitting diodes (LEDs) in the moving control surface mounted on the leading edge of the wing. This arrangement is applicable to slat-style control surfaces, in particular, yet is possible for any surface with an in-use orientation suitable for the required light distribution.
An array of LEDs, numbering as required to produce the required light intensity, is fitted to one or more areas of a wing's forward control surface. The light intensity is limited only by the surface area devoted to the array. In a practical case, the protective lens and thermal management solution limit the array size by the resultant weight of the assembly. Because of the erosion effects of high-speed airflow, forward-facing lenses are typically glass. The rather high density of glass makes the lens a significant portion of the light assembly's weight. The current state-of-the-art LED products are a balance between how hard the devices are driven and the thermal efficiency. LEDs are more efficient as the drive current drops. There is a best-case point at which the light output and the thermal losses with the resultant heat dissipation features are reached. In a prototype design, the light assembly is fitted to the inboard slat only. This inner slat is constructed of aluminum materials or a thermally conductive composite material to allow the aircraft structure to buffer the temperature rise in the LEDs and dissipate the heat into the air flowing over the wing. The remainder of the wing surfaces are unaffected and can be constructed of metallic or nonthermally conductive composite material, as desired by the airframe designer.
Adding the light assembly's weight to the slat assembly typically does not require changes to the control surface mechanical systems. The added weight of the light assembly is typically insignificant in relationship to the forces applied from airflow at a typical maximum 250 knots airspeed for deployment.
Preferred and alternative embodiments of the present invention are described in detail below, with reference to the following drawings:
As shown in
The fixed light assembly is preferably one that would be used in a slat that does not rotate between a stowed and a deployed position. In other words, as the slat deploys, the slat does not rotate greater than a threshold amount relative to the wing. The variable-pitch LED light assembly is used in a slat that does rotate when deployed. In another embodiment, the variable-pitch LED light assembly is used if one desires manual or automatic control of direction of the light produced by the light assembly from the slat, regardless of slat or wing orientation.
In another embodiment, the aim of the light produced by the light system is independent of the position of the respective control surface or aircraft attitude. A rotary light base is coupled to a drive motor or positioner that moves to generate a desired aim for the flight phase. The aim can be determined by local control (e.g., firmware or attitude sensor) or incorporated into a flight management system (FMS) that responds to automated take-off and landing sequence of events. In this embodiment, a processor provides a position signal to a motor based on a control signal received at the processor. The control signal may be one generated at a cockpit user interface device (i.e., a light position controller) or includes information related to flight of the aircraft, position of the slat in which the rotatable light assembly is mounted, and/or angle of attack of the aircraft. The processor executes logic, stored in local memory, for interpreting the received control signal and generating the position signal accordingly. For example, if the processor first receives a 2° nose-up angle-of attack value, the position signal generated by the processor is a −2° nose-down value. Then, when the aircraft transitions to the landing configuration and the angle-of-attack value goes to 8° nose up, the position signal generated by the processor is an −8° nose-down value, thus compensating for the rotation of the aircraft. Of course, the processor can compensate for other factors in order to keep the pattern of light generated by the LEDs at an optimum location. The motor used in this embodiment may be a direct drive stepper motor, a gear driven stepper motor if rotation torque is high enough to necessitate the weight of a gear case, or a servo-drive and encoder. The servo-drive and encoder would be more likely used in an analog control system with an attitude target rather than a FMS controlled system.
In one embodiment where multiple installations of light assemblies are included on a slat section, a common positioner with connecting linkage or independent positioners is used. Independent positioners that are in signal communication with a flight management system (FMS) may be used thus allowing the FMS to increase the vertical light pattern for a portion of the flight profile.
In one embodiment, one array of light assemblies in a slat is aimed a few degrees higher or lower than another array of light assemblies in the same slat. This reduces the peak intensity but increases the vertical pattern. This might be benefitial during a flare to touchdown without requiring dynamic aim control from the FMS. This dynamic aiming allows maximum intensity at a defined location in relationship to a flight deck.
The internal structure shown in the rotary actuator 102 is part of a thermal management system. A rotary tube is filled with an organic phase change material (PCM) to store the thermal energy during operation. Internal fins are used to conduct heat into the poor thermally conductive PCM.
It can also be appreciated that a fixed-mounted LED assembly may be used in one or more of the slats of the aircraft 120. In another embodiment, multiple LED assemblies are located on one or more slats on a wing.
While the preferred embodiment of the invention has been illustrated and described, as noted above, many changes can be made without departing from the spirit and scope of the invention. For example, The LED light assemblies may be included in other movable control surfaces, such as the flaps, canards, etc. Accordingly, the scope of the invention is not limited by the disclosure of the preferred embodiment. Instead, the invention should be determined entirely by reference to the claims that follow.
Claims
1. A movable control surface device for a vehicle, the device having a control surface portion and a mechanical component for allowing the control surface portion to move relative to a part of the vehicle, the device comprising:
- a light assembly comprising: a lens; a plurality of light-emitting diodes (LEDs); and a housing configured to receive the plurality of LEDs and the lens, wherein the housing of the light assembly is received within the control surface portion, such that the lens is flush with a surface of the control surface portion.
2. The device of claim 1, wherein the light assembly further comprises a plurality of reflectors.
3. The device of claim 1, wherein the plurality of LEDs are rotatably mounted within the housing.
4. The device of claim 3, wherein the light assembly further comprises a control device configured to control position of the LEDs relative to the housing based on a position of the control surface portion.
5. The device of claim 3, wherein the light assembly further comprises a controller configured to control position of the LEDs relative to the housing based on a received control signal.
6. The device of claim 5, wherein the control signal comprises at least one of position of the control surface portion, angle-of-attack of the vehicle, or phase-of-operation of the vehicle.
7. The device of claim 5, wherein the vehicle is an aircraft and the control surface portion is a leading-edge wing slat.
8. The device of claim 7, further comprising a second light assembly mounted within the control surface comprising:
- a lens;
- a plurality of LEDs, wherein the plurality of LEDs are rotatably mounted within the housing; and
- a housing configured to receive the plurality of LEDs and the lens,
- wherein the housing of the light assembly is received within the control surface portion, such that the lens is flush with a surface of the control surface portion.
9. The device of claim 8, further comprising a first positioning device coupled to the first light assembly and second positioning device coupled to the second light assembly, wherein the first positioning device positions the first light assembly to produce a bandwidth of light having a first angular center, wherein the second positioning device positions the second light assembly to produce a bandwidth of light having a second angular center, the first and second angular centers having different values.
10. A method comprising:
- at a controller located within an aircraft, receiving a control signal, wherein the control signal comprises at least one of position of a control surface portion, angle-of-attack of the aircraft, or phase-of-operation of the aircraft; and generating a position signal based on the received control signal; and
- at a light assembly located within a control surface on the aircraft, moving a plurality of light-emitting diodes (LEDs), based on the generated position signal.
11. The method of claim 10, wherein the control surface portion is a leading-edge wing slat.
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Type: Grant
Filed: Apr 19, 2011
Date of Patent: Dec 25, 2012
Patent Publication Number: 20120268959
Assignee: Honeywell International Inc. (Morristown, NJ)
Inventors: David Barnett (Urbana, OH), Jeffrey M. Singer (Springfield, OH), Timothy C. Martin (Urbana, OH)
Primary Examiner: Laura Tso
Attorney: Lowe Graham Jones PLLC
Application Number: 13/090,013
International Classification: F21V 33/00 (20060101);